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E. H. SHERBONDY.

NOZZLE RING.

'APPLICATION HLED APR. '8 19-18.

Patented July 22, 1919;

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awozmg .EAItL H. SHERBONIDY, OF CLEVELAND, OHIO.

NOZZLE-RING.

, Application filed Apri18,1918. Serial No. 227,335.

To all whom it may concern: Be it known that I, EARL HpSHERBONDY, a citizen of the United States, residing at Cleveland, in the county of Cuyahoga and State of Ohio, have invented certain new and useful Improvements in Nozzle-Rings, of which the following is a specification.

This invention relates to a nozzle ring for a gas operated turbine, the object of the invention being to provide a nozzle ring which may be cheaply and quickly manufactured in large quantities. To this end, the parts are stamped out of sheet metal. and assembled by simple mechanical steps. The nozzle ring is intended to be-used in conjunction with a turbine casing of the type shown in my co-pending application, Serial Number 224892, filed March 26, 1918.

Other objects and advantages will appear as the description proceeds.

Referring now to the drawings, Figure 1 is a side view, partly in section, of the nozzle ring positioned in the turbine casing; Fig. 2 is afront view of the nozzle ring; Fig. 3 is a side view of the same; Fig. A is a side view of the nozzle ring before the nozzles are attached; and Fig. 5 is a view on the broken line 5-5 of Fig. 3.

The body of the nozzle ring is formed by an annular element A, WhICll element is flanged at one end as shown at2, for attachment to the turbine casing 3. The other end of this annular element A, which may be made of sheet metal, has stamped-in its other end, a series of depressions-or seats 4,

i the metal being pressed inwardly a distance substantially equal to the thicknessof the metal forming the annular element A. These seats a are arranged equally s aced around the edge of the element A, i eing spaced apart at distances substantially equal to the width of one of the seats 4. The seats 4, moreover, are helically disposed with respect to the longitudinal axis of the annular element A, that is to say, they wind.

around the element A as shown in Fig. 4:. These seats are in the shape of a parallelogram, but in Fig. A appear to taper, due to perspective. The seats 4 may actually be made to taper toward the delivery end of the device, if desired, but keeping in mind the purpose of this invention, that is simpliclty and rapid production, the simpler or parallelogram form, is preferred. 4

Seated in the seats A and fastened thereto Specification of Letters Patent.

blades 5 are pro each blade .5 toward the intake opening of the nozzle, being higher than the other end,

Patented July as, rare.

by riveting, brazing or otherwise are a series of trough shaped or substantially U-shaped nozzle blades 5. The legs of these U-shaped elements extend substantially radially from the center of the annular element and so are not quite parallel as they would be if they were strictly U-shaped. The bight 6 of each nozzle 5, is somewhat flattened and shaped to fit in its respective seat 4. The bight 6 of-each nozzle element, it will be evldent, is curved in such a manner as to conform with the helical curve, already described, of the seat 4. The nozzles 5 are made out of stamped out sheet metal of any desired material.

It will be evident that there is thus provided a series of nozzles, helically disposed with respect to the axis of the annular element A, one set of nozzles being defined between the legs of each U-shaped element 5 and the other set of nozzles, being defined between thepadjacent legs of diiferent U- shaped elements 5.

At the points where the gases enter the nozzles, the legs 5 are bent in a direction ingress of the gases.

'. The outer edges of the several nozzle ledas shown, that part of the edge preferably gradually taperin from the higher part 7 to the lower part 7 The nozzle ring is positioned in the turbine casing '3, as shown in Fig. 1, in such a position as to deliver the gases onto the buckets 8 of the turbine 9. Associated with the casing 3, there is an annular diaphragm D, the purpose of the diaphragm being to guide the gases into the nozzles of the nozzle ring. The inner edge of said diaphragm is accordingly seated on the curved portion 7-7 of the respective blades 5, in such a manner, as to make a gas tight fit. The curve of the portion 77, is such as to conform to the curvature of the inner part of diaphragm D.

The gases enter the turbine casing 3, through the inlet pipe 10, pass through the nozzles 5, through the buckets 8 of the turbine and thence out through the exhaust pipe 11.

It will now be evident that I have'dlsclosed a nozzle ring of extremely, simple construction, one that can be readily stamped out of sheet metal and one which accordingl can be produced in large quantities.

ile I have used the term U-shaped in the claims, it should be understood that the claims are not to be limited strictly to U-shaped construction, but are to cover a structure substantially U-shaped; that is, one in which the legs of the U are not exactly parallel.

It should be understood that the invention may be carried out in other ways, such as fall Within the scope of the appended claims.

I claim- 4 1. A turbine nozzle ring, comprising an annular element, a series of spaced apart U-shaped nozzles positioned thereon, the legs of said nozzles extending substantially radially with respect to the axis of said annular element, the bight of each U of the respective nozzles being in contact with said annular element.

2. A turbine nozzle ring, comprising an annular element provided with spaced apart seats, and nozzles substantially U-shaped in cross-section, the bight of the U of each nozble being seated in its respective seat, the legs of said nozzle extending substantially radially with respect to the axis of said annular element.

3. A turbine nozzle ring, comprising an annular element, a series of spaced apart U-shaped nozzles positioned on said annular element, the bight of the U being in contact with said annular element.

4. A turbine nozzle ring, comprising an annular element, a series of U-shaped nozzles, said annular element being provided with a series of seats spaced apart and shaped to fit the bight of said U-shaped blades, and means for mounting the bight of said U-shaped blades in said seats, wherethe edges of said nozzles being shaped to cooperate with a suitable element to completely define the nozzle channels.

8. The combination as claimed in claim 4, the edges of said nozzles being shaped to cooperate with a suitable element to completely define the nozzle channels.

- 9. A turbine nozzle ring, comprising an annular element, and a series of U-shaped nozzles bent around the outside of said element helically with respect to the longitudinal axis of said annular element to define nozzles helically disposed with respect to the said axis. 7

10. A turbine nozzle ring, comprising an annular element provided with seats, helically arranged with respect to the longitudinal axis of said annular element, and a series of U-shaped nozzles, each having the bight of the U positioned in its respective seat, and means for holding the said nozzles in position.

11. The combination as claimed in claim 1, the two Walls of said nozzles, at one end, being bent about an axis substantially parallel to its respective leg of said U-shaped nozzles.

12. The combination as claimed in claim 1, said nozzles being helically disposed on said annular element, the two walls of said nozzles at one end, being bent about an axis substantially parallel to its respective leg of said U-shaped nozzles.

In testimony whereof I afiix my signature.

EARL H. SHERBONDY. 

